Fluid flow control mechanism

ABSTRACT

A fluid flow control mechanism is provided for linearizing a fluid flow. The mechanism includes a frame having a cylindrical outer baffle which rotatably supports a plurality of propeller elements thereon. Each propeller element defines a respective sweep area as the propeller element is rotated which overlaps sweep areas of adjacent propeller elements. The outer baffle circumscribes an outer periphery of the collective sweeps areas of the respective propeller elements. The propeller elements rotate in the same direction whereby forces of curvature flow of adjacent propeller elements substantially cancel one another to linearize fluid flow through the mechanism. Additional baffles and infills within the areas of non blade sweeps may be provided for particular applications of the mechanism. In various applications, linear forces of vector flow are formed by integrating curvature forces of tangential flow and economy flow systems are formed by integrating curvature forces potentials on the planes of rotating propellers to provide the emission and induction flow with an insulation whereby fluid in the immediate vicinity of the mobile flow remains in an undisturbed static state. This allows a fluid propulsion assembly to be fitted with an outer utility mantle in the static zone of the field.

[0001] The present invention relates to a fluid flow control mechanismarranged to linearize a fluid flow which is particularly suited forapplication in fluid propulsion and in turbines. The mechanism generallycomprises a propeller type propulsion system for either pushing fluid ina substantially linear manner, maintaining fluid flow in a substantiallylinear manner or propelling itself through a fluid along a substantiallylinear vector.

BACKGROUND OF THE INVENTION

[0002] In consideration of the dynamics of fluid kinetics and of aunified field with regard to such, conventional flow machine designs,including pumps, compressors, fans and generators in general, typicallylose considerable efficiency due to an inability to maintain fluid flowtherethrough in a substantially linear manner. Accordingly conventionaldesigns can be improved so as to provide major benefits with regard tomachine efficiency, the required effects concerning desired flowpatterns and flow forces regarding performance and a quietness ofoperation due to the overcoming of turbulence. Consequently,applications of improvements to flow machines can be wide ranging anddiversified within the confines of industry in general.

[0003] In brief, the unified field of fluid kinetics requires thepotentials of energy to be related to a mechanical concept wherebystatic states, and mobile states refer to dimensions of potential forcewith dimensions of potential flow and how these forces with flow relateto a dimension of linear force with vector flow or a of curvature forcewith a tangential flow. It is only by being able to relate these forcesand flows to plane dimensions that flow machines can be designed wherebythe flows and the forces can be transferred between the horizontal andvertical planes without incurring losses of the dimensional force orforces.

[0004] Consequently, a mechanical concept relates the potentials ofenergy to unequal mobile curvature flows with force and the field energyto being the sum total of the two potentials with regards the linearlength of each curve and therefore, the flow machines can be arranged todisplay two unequal field systems within which tangential curvatureflows with force are established, these being the inner field and outerfield, comprised of individual chambers, and by which or from whichperpendicular linear flows are produced with two directions of potentialforce.

[0005] The method by which these flows and forces are able to be eitherstructured, controlled or transferred between or upon planes requiresthe establishment of binary forces and bi-polar flows either by machinedesign set-up to establish such or by machine design set-up to maintainsuch.

[0006] In the either or situation, the forced flow fluid input requiredto power a turbine generator is delivered by a linear flow of fluid.These fluid flows are structured into linear flows by conduits that aresubsequently directed onto impellers so as to rotate a rotor and providemotive curvature force. Typically, turbine generators lose efficiency bynot being able to maintain the inputted flow of fluid in a linear flowby rotary activity of the turbine blades. Alternatively, a fluidtypically is pressured by rotating propellers within a manifold forpropulsion. Typically, air and marine propulsion or hover systems usingrotating planes to either achieve propulsion or hover, lose efficiencyon the unstructured curve of the produced force in the form ofturbulence.

SUMMARY OF THE INVENTION

[0007] According to one aspect of the present invention there isprovided a fluid flow control mechanism for linearizing a fluid flow,the mechanism comprising:

[0008] a generally cylindrical outer baffle arranged to direct flow offluid therethrough in a flow direction substantially parallel to acentral main axis of the outer baffle from an upstream side to adownstream side of the outer baffle; and

[0009] a plurality of propeller elements supported for rotation, eachabout a respective propeller axis, the propeller axes being parallel toone another and the main axis of the outer baffle and being spacedcircumferentially about the main axis;

[0010] each propeller element defining a respective sweep area as thepropeller element is rotated about the respective propeller axis thereofwhich lies perpendicular to the respective propeller axis;

[0011] the propeller elements being located such that the outer bafflecircumscribes an outer periphery of the collective sweep areas of therespective propeller elements and such that the sweep area of eachpropeller element is arranged to overlap the sweep area of adjacentpropeller elements;

[0012] the propeller elements being supported for rotation in the samedirection whereby forces of curvature flow of adjacent propellerelements substantially cancel one another to linearize fluid flow in theflow direction.

[0013] In accordance with one embodiment of the present invention thatdemonstrates an octonary bi-polar propulsion and hover system thatincorporates an economy flow system, the embodied concept candemonstrate how linear forces of vector flow are formed by integratingcurvature forces of tangential flow and how economy flow systems can beestablished to increase force potentials on the planes of rotatingpropellers and provide the emission and induction flow with aninsulation whereby fluid in the immediate vicinity of the mobile flowremains in an undisturbed static state, allowing the propulsion/hoverassembly to be fitted with an outer utility mantle in the static zone ofthe field and thereby, provides the octonary bi-polar propulsion/hoversystem with two useful utility areas. One embodied concept described asfollows relates to an integral eight propeller set-up that is situatedwithin a manifold above a series of arranged baffles.

[0014] Turbine generators using an integral impeller set-up with nointernal economy flow system because the flow is already structuredwould gain in efficiency using the present invention by being able tokeep the flow linear by rotary activity. Air and marine propulsion orhover systems using the present invention would produce a structuredlinear force with vector flow and thereby, achieve far greaterefficiency with an overall improved effect with regards the flow notimpinging upon the immediate surrounding area.

[0015] The internal economy flow system featured within the design ofthe embodied concept demonstrates a method of increasing propellerpropulsion and improving an ability to control hover by using binaryoscillating forces of bi-polar flows to connect plane dimensions. It isalso demonstrated how these internal economy flows form individualconduits of flow within the main flow that collectively provide the mainlinear vector flow with a well defined flow pattern that is isolated bya boundary layer from the immediate surrounding area.

[0016] Each propeller element, in one embodiment, may comprise a pair ofdiametrically opposed blades. These propeller elements are preferablyall supported for rotation within a common plane, rotation of eachpropeller element being fixed in timing with rotation of adjacentpropeller elements to avoid collision of the propeller elements at theoverlapping sweep areas.

[0017] The propeller axes are preferably fixed in position relative toone another.

[0018] Alternatively, when the propeller elements each comprise aplurality of blades, specifically more than two, each propeller elementis preferably rotatable within the respective sweep area which isparallel and spaced in a direction of the main axis from the overlappingsweep areas of adjacent propeller elements.

[0019] The sweep area of each propeller element may overlap the sweeparea of adjacent propeller elements within a range of 40% to 60% of alength of the blades of the propeller elements, but is preferablyoverlaps by approximately 50% of a length of the blades.

[0020] There may be provided a generally cylindrical inner baffleinscribed within an inner periphery of the collective sweep areas of therespective propeller elements.

[0021] The propeller elements are preferably located relative to oneanother such that an unswept cross sectional area between the inner andouter baffles is substantially equal to an overlapping portion of thesweep areas of the propeller elements.

[0022] The inner and outer baffles at the upstream side of the outerbaffles preferably extend in a direction of the main axis beyond thepropeller elements.

[0023] The outer baffle may include a shelf extending radially outwardtherefrom a distance substantially equal or greater than a diameter ofone of the sweep areas of the propeller elements.

[0024] In one arrangement, there is provided 8 propeller elementssupported at even circumferential spacings between the inner and outerbaffles, a cross sectional inner area spanning the inner baffle beingsubstantially equal to the sweep area of one of the propeller elements.

[0025] The inner area spanning the inner baffle is preferably enclosed.

[0026] There may be provided a driving motor housed within the innerarea for driving rotation of the propeller elements.

[0027] Alternatively, there may be provided a driven rotor housed withinthe inner area for being driven by rotation of the propeller elementswhen supported in a moving fluid.

[0028] The inner area may also house common gearing coupling thepropeller elements for rotation together at a predetermined timingrelative to one another.

[0029] There may be provided a cylindrical central baffle concentricallyspaced between the inner and outer baffles, the propeller axes beinglocated at spaced positions about the central baffle.

[0030] A plurality of radial baffles preferably extend in a radialdirection of the main axis between the inner and outer baffles andsupport the central baffle.

[0031] Each propeller axis may be located at an intersection of thecentral baffle and a respective one of the radial baffles.

[0032] The central baffle and the radial baffles are preferablysupported on a downstream side of the propeller elements.

[0033] An unswept area between the outer baffle and the collective sweepareas of the propeller elements may be enclosed or filled by contouredinfills which surround the collective sweep areas of the propellerelements, the contoured infills being in relief and fixed with respectto the outer baffle.

[0034] The contoured infills are preferably tapered to be substantiallyflush with the outer baffle as the contoured infills extend in adirection of the main axis away from opposing sides of the propellerelements.

[0035] There may be provided a central infill spanning a central unsweptarea surrounded by the collective sweep areas of the propeller elements,the central infill being tapered towards opposing apexes along the mainaxis on opposing sides of the propeller elements.

[0036] In a turbine generator configuration, the central infillpreferably houses a rotor which is coupled to the propeller elements soas to be driven by rotation of the propeller elements. Length of theblades preferably increases in the flow direction in this instance.

[0037] Each propeller element may comprise a plurality of blades atvarious positions about a full circumference of the propeller element,the blades of each propeller element being rotatable in one or moreplanes which are offset in a direction of the main axis from the bladesof adjacent propeller elements.

[0038] There may be provided four propeller elements supported at evenlyspaced positions about the main axis, an inner periphery of each sweeparea being intersected by the main axis. There is provided a generallycylindrical central baffle intersecting the propeller axes and aplurality of radial baffles extending in a radial direction of the mainaxis and supporting the central baffle, the radial baffles intersectingone another at the main axis.

[0039] Preferably, the propeller elements are rotatably supported on aframe with the propeller axes in fixed relation to one another and theframe, the frame being supported for rotation about the main axis.

[0040] In a turbo fan-jet compressor configuration, the mechanismpreferably further comprises:

[0041] contoured infills enclosing an unswept area between the outerbaffle and the collective sweep areas of the propeller elements, thecontoured infills surrounding the collective sweep areas of thepropeller elements and being tapered on opposing sides of the propellerelements towards the outer baffle;

[0042] a central infill spanning a central unswept area surrounded bythe collective sweep areas of the propeller elements, the central infillbeing tapered towards the main axis on opposing sides of the propellerelements;

[0043] a cylindrical central baffle concentrically spaced between thecentral infill and the outer baffle, the propeller axes being located atspaced positions about the central baffle; and

[0044] a plurality of radial baffles extending in a radial direction ofthe main axis between the central infill and outer baffles andsupporting the central baffle.

[0045] Each propeller element may comprise a plurality of pairs ofdiametrically opposed blades which are stacked along the propeller axisat various angles relative to one another in a helical configuration,each blade having an equal angle pitch of no more than 45 degrees.

[0046] When the blades of each propeller element lie in a common planewith corresponding blades of adjacent propeller elements, the propellerelements are preferably rotated together at a predetermined timingrelative to one another to avoid collision of adjacent propellerelements having overlapping sweep areas.

[0047] In a polarizing unit configuration for production of plasma bylow temperature gas fusion, the mechanism preferably further comprises:

[0048] a generally cylindrical inner baffle inscribed within an innerperiphery of the collective sweep areas of the respective propellerelements;

[0049] a generally cylindrical central baffle concentrically spacedbetween the inner and outer baffles; and

[0050] a plurality of radial baffles extending in a radial direction ofthe main axis between the inner and outer baffles and supporting thecentral baffle;

[0051] at least one of the baffles including a passage for receiving acooling fluid to be circulated therethrough.

[0052] In the polarizing unit configuration, each propeller elementpreferably comprises a pair of diametrically opposed blades, each havinga pitch angle of less than 45 degrees, the sweep area of each propellerelement overlapping the sweep area of adjacent propeller elements byapproximately 50% of a length of the blades of the propeller elements.

[0053] There may be provided six propeller elements which are supportedfor rotation within a generally common plane, rotation of each propellerelement being fixed in timing with rotation of adjacent propellerelements to avoid collision of the propeller elements at the overlappingsweep areas.

[0054] In the polarizing unit configuration, the mechanism is preferablyin combination with a sealed spherical vessel into which gases arepulsed at intermittent intervals and plasma is extracted.

BRIEF DESCRIPTION OF THE DRAWINGS

[0055] In the accompanying drawings, which illustrate an exemplaryembodiment of the present invention:

[0056]FIG. 1 is a perspective view of a top side of the fluid flowcontrol mechanism.

[0057]FIG. 2 is a perspective view of a bottom side of the mechanismaccording to FIG. 1.

[0058]FIG. 3 is a schematic top plan view illustrating the relationshipof the propeller elements of the mechanism according to FIG. 1.

[0059]FIG. 4 is a top plan view of the mechanism according to FIG. 1shown with a suitable drive mechanism connected between the propellerelements.

[0060]FIG. 5 is a perspective view of one of the propeller elements.

[0061]FIG. 6 is a schematic top plan view of the mechanism illustratingthe overlapping sweep areas of the propeller elements and theoscillating looped potentials of tangential force.

[0062]FIG. 7 is a side elevational view of one of the propeller elementswhich illustrates the mobile flow system of the inner and outerchambers.

[0063]FIG. 8 is a schematic side elevational view of the mobile andstatic field systems in a mechanism according to FIG. 1.

[0064]FIG. 9 is a side elevational view of the mechanism shown rotatablysupported on a fixed frame.

[0065]FIG. 10 is a perspective view of the infills which enclose theunswept areas of the propeller elements between the inner and outerbaffles.

[0066]FIGS. 11A and 11B are respective side elevational and top planviews of the fluid flow control mechanism in a turbine generatorconfiguration.

[0067]FIG. 12 is a sectional view of the fluid flow control mechanism inan inline pump configuration.

[0068]FIG. 13 is a top plan view of a propeller element for use with thefluid flow control mechanism in a turbo fan jet compressorconfiguration.

[0069]FIG. 14 is a schematic top plan view of one embodiment of themechanism in which only four propeller elements are provided.

[0070]FIG. 15A is a schematic side elevational view of the fluid flowcontrol mechanism in a polarizing unit configuration.

[0071]FIG. 15B is a top plan view of the mechanism according to FIG.15A.

DETAILED DESCRIPTION

[0072] Referring to the accompanying drawings there is illustrated afluid flow control mechanism generally indicated by a reference numeral10. The mechanism 10 is particularly useful for linearizing fluid flowto increase efficiency in pumps, turbines, compressors or fans and thelike. The mechanism is suitably arranged to either push fluid in alinearized fashion, maintain fluid in a linearized fashion or ifrequired propel itself through a fluid on a linear vector. While pluralembodiments are illustrated and described herein, the common elements ofthe various embodiments will first be described herein.

[0073] The mechanism 10 includes a frame 20 which supports a pluralityof propeller elements 22 thereon. Each propeller element 22 includesradially extending blades 24 which are supported for rotation within ablade sweep area 26 lying perpendicular to a respective propeller axis28 about which the propeller element is rotated. The frame 20 includes amain axis 30 about which the propeller elements are circumferentiallyspaced evenly from one another and the main axis. The propeller axes 28are parallel to the main axis 30 of the frame with the propellerelements being supported on the frame so that the axes 28 remain infixed position relative to one another. The sweep areas 26 of therespective propeller elements are arranged to overlap one another byapproximately 50 percent of the length of each blade 24. The bladesfurther include a pitch angle which is equal or less than 45 degrees.

[0074] The frame 20 includes an outer baffle 32 which is cylindrical inshape, being concentric with the main axis 30 of the frame. The outerbaffle is arranged to circumscribe the collective sweep areas 26 of thepropeller elements so that an outer peripheral edge of the sweep area 26of each propeller element lies directly adjacent to the outer baffle 32.Height of the outer baffle 32 in the longitudinal direction of the mainaxis 30 is arranged to project beyond the propeller element 22 in bothdirections.

[0075] Fluid motion relative to the frame 20 of the mechanism 10 passesthrough the mechanism so as to remain generally linear from an upstreamside 34 to a downstream side 36 of the frames, generally parallel to themain axis of the frame.

[0076] Turning now to the first embodiment illustrated in FIGS. 1through 8, eight propeller elements 22 are illustrated. An inner baffle38 which is cylindrical in shape and supported on the frameconcentrically with the main axis, is inscribed within the collectivesweep areas 26 of the propeller elements so as to surround a centralunswept area 40. When eight propeller elements 22 are provided, thecentral unswept area 40 is approximately equal to the sweep area 26 ofone of the propeller elements. An unswept portion of the cross sectionalarea between the inner and outer baffles is arranged to be approximatelyequal to the overlapping sweep areas of the propeller elements.Similarly to the outer baffle, the inner baffle 38 also extends in thelongitudinal direction of the main axis beyond the propeller elements 22in both directions.

[0077] A central baffle 42 is provided which is cylindrical and alsoconcentrically mounted about the main axis 30 of the frame. The centralbaffle 42 is arranged to be spaced centrally between the inner and outerbaffles so as to intersect the respective propeller axes 28, with theaxes 28 being spaced evenly circumferentially thereabout.

[0078] Radial baffles 44 are provided which span in a radial directionof the main axis 30 between the inner baffle 38 and the outer baffle 32.The radial baffles 44 lie parallel to the flow direction and the mainaxis 30. At an intersection of each radial baffle 44 and the centralbaffle 42, a rotary housing 46 is mounted for rotatably supporting oneof the propeller elements 22 thereon for rotation about its respectivepropeller axis. The radial baffles 44 support the central baffle, theinner baffle 38 and the propeller elements 22 on the outer baffle 32.The central baffle 42 and the radial baffles 44 are supported downstreamform the propeller elements to avoid collision with the propellerelements.

[0079] The outer baffle may include a shelf extending radially outwardtherefrom a distance substantially equal to or greater than a diameterof one of the sweep areas of the propeller elements.

[0080] A drive mechanism 48 is supported on an upstream side of thepropeller elements 22 for coupling the propeller elements to rotatetogether. A motor is housed within the central area 40 to which thedrive mechanism 48 is coupled. The drive mechanism 48 includes a seriesof idler pulleys and belts which interconnect between the output shaftof the motor and the propeller elements.

[0081] In the first embodiment, each propeller element 22 includes twodiametrically opposed blades which are supported for rotation in acommon plane with the blades of the remaining propeller elements.Accordingly, due to the overlapping sweep areas 26, the propellerelements are arranged to be rotated in a fixed timing sequence relativeto one another to avoid collision of the blades of the propellerelements. When eight propeller elements are provided each having twodiametrically opposed blades, the propeller elements are arranged to beoriented at right angles to the blades of adjacent propeller elementsduring complete rotation thereof.

[0082] When supported in an open configuration, depth of the baffles,also referred to as height of the baffles in the axial direction of themain axis, is proportional to the angle of pitch of the propellerelements, and more specifically the amount of air displaced by thepropeller elements. The propeller elements displace a volume of throughflow in accordance to each blade and the baffle depth/height is inaccordance to each propeller element's amount of displacement of onerevolution for optimum interference of the given through flow. In oneexample, each blade is 8 inches in length at a pitch angle of 45degrees. Two such blades provide a 16 inch diameter sweep area and onone revolution each blade displaces, as it were, 8 linear inches offluid that is divided by 4 to arrive at 2 inches per section of eachblade and therefore, 4 inches per section for two blades. The innerbaffle depth is therefore 4 inches in this example. The inner field area103, being a condensed area in relation to area 106, requires the fullbaffle depth, whereas the outer field area 106, due to being lesscondensed and having to supplement the inner field 103 by the economyflow system and facilitate flow with regard to the exterior outer flow,is able to be of less depth. This less depth is calculated from a 45degree propeller that pushes a cubic proportion of fluid through thehorizontal plane of the propeller elements in relation to the diameterof the sweep area. The central point of the inner and outer cube areasis in relation to a horizontal line extending from the tip of one bladeat its inner most central position to a position equal in distance fromthe outer tip of the opposite blade i.e. midway between these two pointsor at the outer blade tip. This outer distance i.e. equal to thediameter of the blade sweep area, is the absolute of the outer fieldwith regard to the dynamics of the inner mobile flow i.e. the staticboundary layer occupies this outer dimension in definition. The cubicproportion of fluid, being broken into 4 sections, descends beneath theplane of the propellers only one quarter in the above example, that isonly 4 inches of a 16 inch through flow of one revolution. A line takenfrom the first quarter of the cube at the inner most point beneath thepropellers to the outermost point of the static field on the horizontalplane of the propellers thereby represents the required interferencewith regard to the mobile inner flow. Less propeller pitch therebyequates to less baffle depth. In some instances, the propeller elementsmay have an adjustable blade pitch angle, in which case the bafflesadjust in length to compliment the blade pitch angle adjustment.

[0083] Turning now to the embodiment of FIG. 9, the mechanism issimilarly arranged to the previous embodiment, with the exception thatthe outer baffle be rotatably supported on a fixed support frame 50 bysuitable bearings 52 and the like to permit rotation of the entiremechanism relative to a fixed frame. A suitable actuator is provided forcontrolling rotation of the entire mechanism about the main axis thereofrelative to the support frame. When the frame of the mechanism 10 isrotatable relative to a fixed frame, rotation of the propeller elementsmay alternatively be provided by mounting a planetary gear on eachpropeller element, for rotation therewith, which meshes with astationary central gear about which the mechanism 10 and the propellerelements are rotated. Rotation of the mechanism relative to thestationary gear when the respective planetary gears of the propellersare coupled to the stationary gear causes rotation of the propellersabout their respective propeller axes with the planetary gears as themechanism is rotated. The ratio of revolutions of the propeller elementsrelative to the revolutions of the mechanism is determined by the gearratio coupled the planetary gears to the stationary central gear. Theplanetary gear and central gear driving mechanism of the propellerelements is also operable in mechanisms having four or six propellerelements and in instances where the frame of the mechanism 10 remainsstationary, but the central gear rotates instead.

[0084] Turning now to the embodiments of FIGS. 10 through 12, variousapplications of the mechanism are illustrated in which outer infills 54and a central infill 56 are provided. The outer infills 54 are supportedon the outer baffle 32 in relief thereto to enclose the unswept areasbetween the collective sweep areas of the propeller elements and theouter baffle 32. Similarly the central infill 56 is supported at theinner baffle to span an unswept area in contour with the surroundingcollective sweep areas of the propeller elements.

[0085] As illustrated in FIG. 10, the outer infills 54 and the centralinfills 56 are shown in combination with the inner baffle 38, thecentral baffle 42 and the radial baffles 44 which are supporteddownstream from the propeller elements which the infills surround. Thisarrangement of infills in combination with baffles may be useful forpumping configurations, turbine compressors or turbo fan jetcompressors, each of which includes varying blade types on therespective propeller elements.

[0086] Turning now to FIGS. 11A and 11B, a turbine generator isillustrated which includes outer infills 54 and central infills 56 asdescribed above. In this instance, the central infill houses a drivenrotor 54 having a power takeoff mechanism for drawing power therefromwhen the rotor 54 is rotated as a result of being coupled to therespective propeller elements to rotate therewith by suitable gearing 59which is also housed within the central infill.

[0087] The propeller elements in this instance include plural blades 24supported at plural angles relative to one another within each ofseveral planes which are stacked in spaced orientation relative to oneanother in an axial direction along the respective propeller axis. Eachplane of blades of each propeller element is arranged to be spaced inthe axial direction from a plane of blades of adjacent propellerelements that are overlapped.

[0088] Each propeller element further includes a core 60 which isgenerally frustoconcial in shape tapering from a larger diameter at theupstream side to a smaller diameter at the downstream side so as totapered with the flow direction. The blades 24 project radially from thecore of the respective propeller elements so as to have a slightlyincreases outer diameter so that the blades nearer to the downstreamside are longer than those adjacent the upstream side.

[0089] In the embodiment of FIG. 12, the mechanism is suitably arrangedfor being supported as an inline pump for a pipe. The mechanism includesa pipe section 62 having conventional bolt flanges 64 at each endthereof for being bolted in series with a pipeline. Infills 54 and 56are provided as described above. The central infill houses a motor 66for driving rotation of the propeller elements. The central infill isenclosed about the motor 66 and tapers to a pair of opposing apexes 68along the main axis on opposing sides of the propeller elements.Similarly the outer infills 54 taper outwardly towards the outer baffleor the inner walls of the pipe section 62 in this instance, so as to besubstantially flush therewith at a location spaced outwardly from eachside of the propeller elements.

[0090] Turning now to FIG. 13, a propeller element 22 is illustrated foruse in a turbo fan jet compressor having infills and baffles asillustrated in FIG. 10. In this instance each propeller elementcomprises a shaft 70 upon which a plurality of blades 24 extend radiallyoutwardly therefrom. The blades are stacked along the shaft 70 in pairsof diametrically opposed blades which are offset angularly slightly fromadjacent pairs of blades so that the blades collectively are in agenerally helical and spiral formation. Each blade of each propellerelement is oriented to be perpendicular to a corresponding blade ofadjacent propeller elements which are in a common plane therewith, withthe propeller elements being maintained to rotate in a fixed timingsequence relative to one another so as to avoid collision of the bladesof the propeller elements. The pitch angle of the blades in thisinstance are equal or less than 45 degrees.

[0091] Turning now to the embodiment of FIG. 14, a mechanism 10 isillustrated in which only 4 propeller elements are provided withoverlapping sweep areas similarly to the previous embodiments. The sweepareas are arranged to overlap one another so that an inner peripheraledge of each sweep area intersects a dead center 72 of the mechanism. Inthis arrangement radial baffles 44 are similarly provided as in theprevious embodiments, however the baffles are arranged to intersect atthe dead center and extend radially outwardly to the outer baffle 32. Acentral baffle 42 is again provided, spaced between the dead center 72and the outer baffle so that one of the propellers is located at anintersection of a respective radial baffle 44 and the central baffle 42.

[0092] As illustrated in FIGS. 15A and 15B, in a further embodiment ofthe control mechanism 10, the mechanism may form part of a bipolarpolarizing unit in the form of a research and development piece ofequipment for the production of plasma by low temperature gas fusion. Inthis instance the mechanism is supported within a sealed chamber 76 intowhich gas is injected by an injector 78 and plasma is extracted at anoutlet 80.

[0093] As illustrated in FIG. 15B, the mechanism in this instanceincludes six propeller elements 22 having sweep areas 26 which overlapthe areas 26 of adjacent propeller elements by approximately 50 percentof the length of the blades which corresponds to approximately ¼ of thediameter of the propeller element. Similarly to the first embodiment, aninner baffle 38 is inscribed in the collective sweep areas with acentral baffle 42 being supported spaced concentrically between theinner and outer baffles and radial baffles 44 being provided which spanbetween the inner and outer baffles supporting the central bafflethereon. The baffles in this instance however differ in that the bafflesare hollow and include passages extending there through for receiving acooling fluid to be circulated there through as required for cooling ofthe baffles. A fluid circulating mechanism 82 is provided incommunication with the passages 84 in the baffles to control circulationof the cooling fluid there through. In this embodiment, the propellerelements each include a pair of diametrically opposed blades whichrotate in a common plane with blades of adjacent propeller elements soas to require a fixed timing sequence which synchronizes rotation ofadjacent propeller elements to be offset from one another by 90 degreesas described above. Each blade has a pitch angle of less than 45 degreesas in previous embodiments. In operation gases are injected in pulses atintermittent intervals permitting plasma to be extracted from the sealedchamber 76.

[0094] As noted above with regard to the first embodiment, the 16propeller blades that overlap one with another in the first embodimentand have a pitch angle of 45 degrees, are mounted in a fixed 90 degreetiming sequence upon 8 rotors or propeller elements that are positionedcircumferentially around a common main axis within respective pivotmounts at an intersection of the circular, central baffle and arespective one of the radial baffles.

[0095] When power is supplied to the rotors or propeller elements by anelectric motor via a belt drive transmission system in the firstembodiment, the propeller blades rotate, drawing air down from above ontangents of spiral flow 100 into the manifold of baffles and driving theair into the inner chambers 102 of the inner mobile field system 103 andthe outer chambers 104 of the outer mobile field system 106. Withinthese chambers, the air oscillates on tangential forces 108 on eitherside of the central baffle within the mobile field system 103,106.

[0096] This creates added pressures beneath the propeller elementsbecause as the oscillating tangential forces 108 exit the bafflearrangement on either side of the central baffle, they collide causingthe binary flow of the main mobile field 103,106 of flow to becomelinear and perpendicular to the propeller elements.

[0097] This transformation of the mobile tangential forces of curvatureflow 108 to the mobile linear flows creates two continuous loops ofbackflowing air 110 referred to as the economy flow system within themain flow of the mobile field 103,106. One of these continuous loops ofbackflowing air 110 that pertains to the inner field system 103, cyclesbetween the planes of the propellers within the unswept areas 112 of thepropeller sweep that are bordered by the inner baffle and the propellersweep areas 114. The other loop of backflowing air 110 pertains to theouter field system 106 and it cycles between the inner field and theouter field by circumscribing the central baffle and cycles the plane ofthe propellers within the unswept areas of propeller sweep that arebordered by the outer baffle and the propeller swept areas.

[0098] This economy flow system 110 within the main flow of the mobilefield 103,106 provides the propellers with an increase in thrustpotential by causing a delay in the separation of the air from thelifting surfaces of the propellers and also this economy flow systemestablishes a static field of non flow within the inner areas 124 of themain flow of the mobile field on both sides of the propellers plane ofhorizontal sweep and it also establishes a static field of non flowwithin the outer areas 126 of the main flow of the mobile field on bothsides of the propellers plane of horizontal sweep.

[0099] These static fields of non flow 124, 126 together with the mainflow of the mobile field system establishes and constitutes on eitherside of the propeller planes, one quarter of the unified field of thepropulsion/hover system comprised of the absolute positive forces ofmobile linear flows 128, the absolute positive forces of staticcurvature flows 130, the absolute negative forces of mobile linear flows132 and the absolute negative forces of static curvature flows 134.Thereby, the octonary bi-polar propulsion/hover system achieves 8neutral potentials of a mobile vertical linear force and 8 neutralpotentials of a static horizontal curvature force.

[0100] This outer static neutral field of non flow 126 and inner centralstatic neutral field of non flow 124 provide the octonarypropulsion/hover assembly with strategic areas that can be utilized inthe design of an air/hover craft vehicle. In order to facilitate thedynamics of free flight/hover with regards engine torque an interrelatedsystem of power is required within the inner central area of non flow124. Such a propulsion/hover system complete with static utility mantle136 as featured in the embodied concept of the invention would, as afully developed air/hover craft vehicle, provide a tremendous potentialof lift due to its strong geometric structure of design and its methodof achieving a binary system of vector propulsion. This would alsoprovide optimum stability for vertical take-off and landing with hovercapability. An interchangeable carrier system to facilitate a variety ofuses. A multiple engine system would allow for engines to be serviced orreplaced during flight. The present invention would also provide a veryquiet low noise level propulsion system due to the unified linear andcurvature flow system of the force field. Less fuel consumption thanconventional methods of flight may be expected due to the linear vectorforces of flow.

[0101] To embody the concept into the design of a pump, such a pumpwould provide a continuos high volume, steady state, full linear flow atthe intake and delivery of the flow because no turbulence is created bythe integral rotary action of the blades within the pump. No internaleconomy flow system is required when used as a pump.

[0102] The motor to drive the pump is installed within the centralposition of the pump or situated externally. The blades are two or moreper rotor or propeller element of a 180 degree spread or less and anangle pitch to compliment the viscosity of the fluid and the requiredvelocity flow with regards power input.

[0103] Where the areas of blade none sweep occur, contoured infills arerequired as described above so as to provide a smooth delivery of fluidinto the integral blading system. Also the transmission system to theblading arrangement can be by gears situated on the inflow side upstreamof the discoid. The contoured infills compliment the pitch angle of theblades. The contoured infills compliment the fluid flow and pressuredensities during the inflow, the through-flow and the outflow of thefluid as it passes through the pump.

[0104] To embody this concept into the design of a flow meter, such ameter would create no turbulence with the flow being metered andthereby, provide greater accuracy of a metered flow. The design would bethe same as that of a pump with a transmission system fitted to a meter.

[0105] To embody this concept into the design of a turbine generator asdescribed above, such a generator would not require the inclusion ofstators to control flow as the flow would be controlled by the integralrotary action of the impeller blades. The blades would be stacked in analternate tier stacking format so that as the blades rotate upon eachrotor, they pass between the rotational planes of one another andthereby by rotary activity keeps the flow of fluid substantially linearin format. Also, the turbine configuration does not require the bi-polarassembly using the baffle arrangement of the first embodiment beneaththe integral impeller blade set-up, but does require contoured infillsto infill the non sweep areas of impeller activity. The reason for thenon requirement of the bi-polar baffle assembly beneath the impellers isbecause the fluid is already structured by conduits into linear flowsand the contoured infills in situ with the integral impeller actionkeeps the flow of fluid linear throughout the throughflow of thegenerator configuration.

[0106] To embody the concept of the present invention into an integralbi-polar mixer or blender, such a configuration would provide a methodwhereby a total mix of the entire vat contents would be mixed andblended by two interrelated flows of variable flow velocity that wouldcompliment one another and in doing so maintain a control of thematerials being mixed and blended without the need of flow shields.

[0107] To embody the concept of the present invention into the design ofa fan or blower whereby the whole assembly is able to achieve variablestates of rotation, in the same plane of rotation as that of the bladeassembly, the mechanism has the ability to deliver variable types offlow from described herein as Type 1. through to Type 3.

[0108] In Type 1, steady state, full linear flow is achieved with theflow mechanism, similar to as if, the dispensed fluid is flowing withinan enclosed conduit in which there is no flow outside of the immediatearea of flow. This linear type flow continues until it hits the targetarea and is ideal for wind tunnel testing to be undertaken without theneed of constructing an enclosed rigid structure, for example a tunnel,to contain the wind. To achieve this flow pattern, the support frame ofFIG. 9 is static when in operation and only the propeller elements arerotated.

[0109] In a Type 2 operation, semi-steady, semi-linear flow is achievedwith the mechanism to deliver a flow with a degree of curvature flow andthereby, provide a well defined isolated area of circulating fluidwithin a greater volume of space. To achieve this flow pattern, themechanism is rotated slowly about the main axis on its support frame,shown in FIG. 9, while in operation.

[0110] In a Type 3 operation, non-steady, non-linear flow is achievedwith the mechanism to maximize fluid intake at the expense of losing adefinition of linear flow and thereby, the mechanism achieves a veryhigh velocity full flow intake and provides a blower with acomparatively small area intake to be able to deliver a large volumeoutflow at the blower head. To achieve this flow pattern the mechanismis rotated very quickly about the main axis on the support frame of FIG.9 while in operation.

[0111] These states of flow also apply to air/marine propellerpropulsion systems, providing such with unique features that arereflected in improved performance with an overall increase in energyefficiency

[0112] The internal flow with force relates to an understanding wherebypotential energy can be comprehended as mobile and static mantles thatin turn can represent the dimensions of mobile wave energy and staticcorpuscle energy with regards a unified field in which these potentialsof energy alternate dimensions by flowing in a loop between planedimension. When these looped potentials are unified into a fourdimensional field, the field is unified in a quadruplet formatconsisting of four loops with two poles of eight potentials.Consequently, the economy flow system of the embodied concept, beingoctonary, provides a unified field of sixteen loops with two poles andthirty two potentials.

[0113] Also the propeller timing sequence that involves the setting ofthe propellers at a 90-degree angle to one another is important withregard to achieving four areas of compression within each chamber by a360 degree propeller sweep and four corresponding areas of expansionabove each chamber that are connected by circuits of flow that flowwithin the main linear flow of the field and thereby, by resolutionthese circuits contribute added dimensions and structure to the field inthe form of added pressures provided by four dimensions per circuit i.e.two vertical and two horizontal, that represent flow fields of unequalpotentials. And it was with regard to this resolution of flow pertainingto the flow fields of multiple electric generator set-ups regardingarmature rotation timing sequences to achieve motive electronicpropulsion by forming quadruplet field potentials of structured volumeand size potentials of ‘curvature’ force energy that the embodiedconcept with regard to such an internal economy flow system wasincorporated into the design of this propulsion/hover device.

[0114] This invention relates to and demonstrates the static and mobile,mechanics of energy interaction. The multiple blade system with regardsthe integral rotor set-up is referred to as a discoid. The discoid hasan optimum blade overlapping sweep of 50% within the areas of bladesweep. This 50% overlapping sweep of the blades with regard to beingoptimum is in reference to performance that in turn is related to thebasic quadruplet discoid set-up, that pertains to the four dimensions ofmobile energy within or of two dimensions of static energy. Consequentlythe mechanism is, by design with regard to an attribute of movement,able to deliver variables of flow to suit various requirements withregards fan/blower technology.

[0115] Discoids are formed of bladed rotors that are mountedcircumferentially around a common axis, in such a way, that the bladesoverlap within the areas of sweep.

[0116] The bi-polar assembly/baffle arrangement is a requirement when itis necessary to construct a conduit of static energy around the externalareas of the discoid or when an entrapment area of added pressure isrequired beneath the discoid. When no static field is required to beproduced around or exterior to the discoid and no added pressure isrequired beneath the discoid such as when the system is installed as aninline pump, then no bi-polar assembly or baffle arrangement isrequired, but it is necessary to infill the areas of non blade sweepwithin the discoid with contoured infills to compliment the integralaction of the blades because whether fluid is forced through an impellerdiscoid arrangement to turn rotors or is drawn by the blades to create aflow into, through and out of the discoid, as in the case of a turbolinear pump, vertical contoured infills are required.

[0117] Infills are required when fluid represents the mobile energy andthe discoid represents the static force, such as in a pump or a turbinegenerator.

[0118] The bi-polar assembly/baffle arrangement is required, withoutinfills, when the discoid represents the mobile energy and the fluidrepresents the static force, such as in a propulsion/hover unit.

[0119] Both infills and bi-polar assembly or baffle arrangement arerequired when the fluid represents static energy of a mobile potentialand the discoid represents static energy of mobility, such as in aturbine compressor unit.

[0120] The design of the discoid with regards to the number of bladesand the arrangement of blades upon each rotor is dependent upon theapplication. For instance, integral turbine generator setups requiremultiple blades upon each rotor of a 360 degree radial format andtherefore, require alternate blade stacking with regards each rotor sothat the blades are able to rotate and pass between the individualplanes of blade rotation and it is this arrangement together withcontoured infills to compliment the integral impeller blade activitythat the high pressure fluid flow required to turn the rotors is keptlinear without the need of stators. Integral turbine generator set-upsoperate by converting high pressure into low pressure by energyabsorption into rotor rotation.

[0121] Integral turbine compressors require the 90 degree timingsequence format because the fan blades are stacked radially along theaxis of each rotor forming two spirals of 180 degrees upon each rotorand this formation together with a bi-polar assembly/baffle arrangementin the presence of contoured infills to compliment the integral bladeactivity keeps the fluid flow linear and under pressure without the needof stators. Integral turbine compressor set-ups operate by creating highpressure from low pressure by rotor rotation/energy input.

[0122] Integral turbine pumps also require the 90 degree timing sequenceformat with regards the blading arrangement, that can involve two bladesper rotor of a 180 degree radial linear spread, each blade at an anglepitch of 45 degrees or less in the presence of contoured infills tocompliment the integral blading activity and the inflow, the throughflow and the outflow of the fluid.

[0123] Contoured infills, when in a discoid system that draws the fluidinto, through and delivers it out of the system such as a pump, arecontoured in two dimensions horizontally and vertically, to complimentthe sweep of the blades, the angle of pitch and the resultant flow ofthe fluid. Also the transmission system is preferably by gears situatedout of the interacting forces with regards the delivery system.

[0124] In the above description, binary force refers to a two forcesystem, whereas bi-polar refers to two poles of curvature and linearthat share an axis. The conduits represent static energy. The discoid,in this instance, refers to a multiple integrally bladed propellerelements mounted circumferentially around a common axis.

[0125] As noted above with regard to the first embodiment, there are twopropeller blades per rotor at a pitch angle of 45 degrees, each bladeoccupying the same plane of rotation. There are eight rotors mountedcicumferentially around a common axis above an arrangement of baffleswithin a manifold. This configuration of the propeller assembly set-up,is such that the circumference of all eight propellers touch acircumscribed line, around the central axis, that encloses a space equalin area to the sweep area of one of the propellers. This arrangementcompliments the required internal economy flow system because of thegeometric relationship between the overlap of the propeller swept areaswith those of the unswept areas within the manifold. The same applies toa quadruplet propeller set-up when the blade tips sweep the dead centerand a line circumscribes the outer area of sweep of the blades. Theunswept areas within the circumscribed area equals the area of thepropeller sweep overlaps.

[0126] Because the blades overlap on the same plane of rotation, theblades are positioned to one another in a fixed 90 degree timingsequence so as to ensure no blade strike occurs. Consequently only twoblades are provided per rotor in the first embodiment. Multiple stackingof this 90 degree format upon each rotor allows for the placement ofmore blades, if more blades are required. When more than two blades arerequired on the same plane of each rotor, the blades are stacked in analternate tier stacking format so that as the blades rotate upon eachrotor they pass between the rotational planes of one another andthereby, no blade strike occurs.

[0127] In the first embodiment, the rotor mounts which rotatably supportthe propeller elements on the frame of the mechanism, are fixed withinthe circular baffle or collar that is perpendicular to the rotationplane of the propellers and that surrounds a common axis. The innersweep areas of the blades are circumscribed by a circular border that isperpendicular to the plane of the propellers and that extends beneaththe plane of the propellers to form a baffle with a depth thatcorrelates to the pitch of the propellers and that extends above theplane of the propellers to form the inner wall of the inductionmanifold. The outer sweep areas of the blades are also circumscribed bya circular border that is perpendicular to the plane of the propellersand that extends beneath the plane of the propellers to form a bafflethat is half the depth to that of the inner baffle and that extendsabove the plane of the propellers to form the outer wall of theinduction manifold. The central circular collar/baffle is in a midwayposition between the outer baffle and the inner baffle and extendsbeneath the plane of the propellers to a depth that compliments both theinner baffle and the outer baffle. This central collar/baffle is fixedin place by a series of perpendicular baffles at each propeller pivotmount, the depths of which conform to the depths of the inner baffle,the outer baffle and the central baffle The same applies to a quadrupletpropeller set-up with the exception that the perpendicular bafflespositioned at each propeller mount join at the dead center.

[0128] The arrangement of the propellers to the baffles is such that airis forced down into the baffles by the action of the propellers andbecause of the configuration of the baffles, to each propeller thedisplacement of air regarding each propeller is broken into fourportions. Because of the overlap of the propellers, the displaced air isdriven into the baffles from alternating directions that portray aninner and an outer propeller stroke with regard to the action of thepropellers as they cross over the central baffle. This propeller actionin situ with the baffles, causes the displaced air within the individualchambers of the baffles to oscillates with a degree of curved tangentialflow. Consequently, the oscillating air in the inner chambers betweenthe inner baffle and the central baffle, oscillates and curves in thesame direction to the air that oscillates and curves in the outerchambers between the outer baffle and the central baffle. Thisoscillation and curved tangential flow of the air within the chambers ofthe baffle arrangement causes the air to undergo a period of entrapmentthat creates an added pressure beneath the planes of the rotatingpropellers. The contours of the propeller swept areas with that of theinner and outer circular baffle is such that strategic areas devoid ofpropeller activity exist, allowing air to flow between the planes of thepropeller rotation in a counter direction to that induced by thepropellers. This activity of flow allows the inner chambers to receiverecycled air from both the inner and outer chambers and thereby, theinner flow of induction is supplemented by a means that increases thethrust of the propellers by delaying the separation of the air from thelifting surface of the propellers. The oscillating air within the innerand outer chambers together with the economy flow system provides theintake and the delivery with a flow of fluid that possesses both qualityand identity. The system of economy provides the inflow and outflow offluid with an insulation that equates as fluid identity and theinteraction of the oscillating force potentials provides the flow offluid with a flow quality that is linear. The reason why this linearflow pattern occurs is due to the descent of the oscillating tangentialforces on either side of the central baffle because as these potentialsof force pass over the central baffle and exit, the tangential forcescollide, in such a way, that the resultant force is perpendicular to theplane of the propellers and thereby, linear in flow and force.

[0129] The mantle extends out from the outer baffle in a horizontalposition that in length is equal to the lengths of two propellers and indoing so defines the static area of the field of the bi-polar flowsystem.

[0130] In the first embodiment, the central circular collar/baffle has adegree of vertical depth that correlates, in depth, to the coaxialvertical baffles of depth and with the propellers angles of pitch. Theinner circular diametrical field baffle has a vertical depth thatequates to the propellers as one quarter of the linear displacementachieved by one such revolution of one of the propellers. The outercircular circumferential field baffle has a vertical depth that equatesto the propellers as one eighth of the linear displacement achieved byone such revolution of one of the said propellers. The radial bafflesare disposed vertically in a radial axis at each propeller element pivotmount, each being connected in the same axial plane and complimentary indepth to the vertical circular inner diametrical field baffle, thevertical circular collar/baffle and the vertical circularcircumferential field baffle and thereby, such baffles form a webarrangement beneath the plane of the propellers. An outer utility mantelof the circular circumferential baffle extends horizontally outwards toa distance that equals, more or less, the combined lateral dimensions ofthe inner diametrical field and the outer circumferential field or theapproximate length of two propeller blades.

[0131] In the integral turbine generator set-up of FIGS. 11A and 11B formaintaining an inputted fluid in a linear flow while providing thegenerator with rotary motive force, the mechanism in this instanceincludes an arrangement of eight propeller elements that support aplurality of blades on each which are stacked in an alternate 360degrees tier stacking format along the linear radial axis of eachpropeller element. The overlap blade sweep is by 50% on respectiveplanes of blade rotation allowing the blades to rotate without incurringblade strike. The propeller elements are typically cone contoured tofacilitate flow. The eight propeller elements are equally spaced andfixed respectively in pivot mounts at either ends around the main axis.Around the inner areas of blade sweep is a close fitting contouredconduit that flares in keeping with the linear radial axis of theimpellers providing a vacant space within the interior of the set-up,within which a propeller element is longitudinally disposed parallel tothe surrounding individual propeller elements for the purpose ofaccepting rotary motive forces from the surrounding individual propellerelements. Around the outer areas of blade sweep, is a close fittingcontoured conduit that flares in keeping with the linear radial axes ofthe impellers and this conduit together with the inner conduitcorrelates so as to form a ventricle that is sealed at one end withinclusions of fluid inlets and that is open at the other end to allowthe fluid to outflow and thereby the through flow of the forced flowfluid input through the ventricle is kept linear by the integral rotaryactivity of the impellers.

[0132] As described above with regard to FIGS. 15A and 15B, a bi-polarpolarizing unit is provided in the form of a research and developmentpiece of equipment for the production of plasma by low temperature gasfusion. In this instance the mechanism comprises an arrangement of sixpropeller elements that support two propeller blades per rotor. Thepropeller blades share the same plane of axial rotation and overlap onewith another by half the blade length within the areas of sweep, eachblade having an angle pitch of no more than 45 degrees and eachpropeller element being fixed in a rigid 90 degree synchronized rotationtiming sequence format. The six propeller elements are fixedrespectively in pivot mounts within a hollow circular collar/bafflearound the main axis in a vertical upright position. An arrangement ofhollow vertical baffles, disposed coaxially and radially, are fixed insitu with the hollow circular collar/baffle beneath the horizontal planeof the propellers. The hollow central circular collar/baffle is fixed inplace by individual hollow radial baffles situated at each rotor pivotmount and that radially connect the hollow outer circularcircumferential baffle to the hollow central circular collar/baffle andthe hollow central circular collar/baffle to the hollow inner circulardiametrical baffle. The hollow outer circumferential bafflecircumscribes the outer areas of propeller sweep. The hollow innercircular diametrical baffle circumscribes the inner areas of propellersweep and by such a hollow bi-polar baffle arrangement is formed wherebyan inner diametrical field of flow comprised of individual chambers andan outer circumferential field of flow also comprised of individualchambers is established and whereby such a hollow baffle arrangement isable to convey a liquefied gas throughout the system and thereby keepthe baffles cool. The bi-polar polarizing unit is installed within abiosphere/sealed spherical vessel into which at intermittent intervalsduring the operating of the equipment gas or gases are pulsed into thebiosphere and plasma is extracted. The baffles are hollow so as tofacilitate a flow of fluid. The mechanism is isolated within the sealedvessel. Fluid is allowed into the environment of the unit inintermittent pulses while the mechanism is operating.

[0133] In this disclosure, there are shown and described only thepreferred embodiments of the invention but it is to be understood thatthe invention is capable of being applied to various other applicationsby those skilled in the art, in a series of combinations andenvironments other than those that have been previously mentioned andaccordingly reference should be made to the appended claims rather thanthe foregoing discussion of preferred examples, to assess the scope ofthe invention in which exclusive rights are claimed.

1. A fluid flow control mechanism for linearizing a fluid flow, themechanism comprising: a generally cylindrical outer baffle arranged todirect flow of fluid therethrough in a flow direction substantiallyparallel to a central main axis of the outer baffle from an upstreamside to a downstream side of the outer baffle; and a plurality ofpropeller elements supported for rotation, each about a respectivepropeller axis, the propeller axes being parallel to one another and themain axis of the outer baffle and being spaced circumferentially aboutthe main axis; each propeller element defining a respective sweep areaas the propeller element is rotated about the respective propeller axisthereof which lies perpendicular to the respective propeller axis; thepropeller elements being located such that the outer bafflecircumscribes an outer periphery of the collective sweep areas of therespective propeller elements and such that the sweep area of eachpropeller element is arranged to overlap the sweep area of adjacentpropeller elements; the propeller elements being supported for rotationin the same direction whereby forces of curvature flow of adjacentpropeller elements substantially cancel one another to linearize fluidflow in the flow direction.
 2. The mechanism according to claim 1wherein each propeller element comprises a pair of diametrically opposedblades.
 3. The mechanism according to claim 2 wherein the propellerelements are all supported for rotation within a common plane, rotationof each propeller element being fixed in timing with rotation ofadjacent propeller elements to avoid collision of the propeller elementsat the overlapping sweep areas.
 4. The mechanism according to claim 1wherein the propeller axes are fixed in position relative to oneanother.
 5. The mechanism according to claim 1 wherein the propellerelements each comprise a plurality of blades, each propeller elementbeing rotatable within the respective sweep area which is parallel andspaced in a direction of the main axis from the overlapping sweep areasof adjacent propeller elements.
 6. The mechanism according to claim 1wherein each propeller element comprises a plurality of blades, thesweep area of each propeller element overlapping the sweep area ofadjacent propeller elements within a range of 40% to 60% of a length ofthe blades of the propeller elements.
 7. The mechanism according toclaim 6 wherein the sweep area of each propeller element overlaps thesweep area of adjacent propeller elements by approximately 50% of alength of the blades of the propeller elements.
 8. The mechanismaccording to claim 1 wherein there is provided a generally cylindricalinner baffle inscribed within an inner periphery of the collective sweepareas of the respective propeller elements.
 9. The mechanism accordingto claim 8 wherein the propeller elements are located relative to oneanother such that an unswept cross sectional area between the inner andouter baffles is substantially equal to an overlapping portion of thesweep areas of the propeller elements.
 10. The mechanism according toclaim 8 wherein the inner and outer baffles at the upstream side of theouter baffles extend in a direction of the main axis beyond thepropeller elements.
 11. The mechanism according to claim 8 wherein theouter baffle includes a shelf extending radially outward a distancesubstantially equal or greater than a diameter of one of the sweep areasof the propeller elements.
 12. The mechanism according to claim 8wherein there is provided 8 propeller elements supported at evencircumferential spacings between the inner and outer baffles, a crosssectional inner area spanning the inner baffle being substantially equalto the sweep area of one of the propeller elements.
 13. The mechanismaccording to claim 12 wherein the inner area spanning the inner baffleis enclosed.
 14. The mechanism according to claim 12 wherein there isprovided a driving motor housed within the inner area for drivingrotation of the propeller elements.
 15. The mechanism according to claim12 wherein there is provided a driven rotor housed within the inner areafor being driven by rotation of the propeller elements when supported ina moving fluid.
 16. The mechanism according to claim 12 wherein theinner area houses common gearing coupling the propeller elements forrotation together at a predetermined timing relative to one another. 17.The mechanism according to claim 8 wherein there is provided acylindrical central baffle concentrically spaced between the inner andouter baffles, the propeller axes being located at spaced positionsabout the central baffle.
 18. The mechanism according to claim 18wherein there is provided a plurality of radial baffles extending in aradial direction from the main axis between the inner and outer bafflesand supporting the central baffle.
 19. The mechanism according to claim18 wherein each propeller axis is located at an intersection of thecentral baffle and a respective one of the radial baffles.
 20. Themechanism according to claim 18 wherein the central baffle and theradial baffles are supported on a downstream side of the propellerelements.
 21. The mechanism according to claim 1 wherein an unswept areabetween the outer baffle and the collective sweep areas of the propellerelements is enclosed by contoured infills which surround the collectivesweep areas of the propeller elements, the contoured infills being inrelief and fixed with respect to the outer baffle.
 22. The mechanismaccording to claim 21 wherein the contoured infills are tapered to besubstantially flush with the outer baffle as the contoured infillsextend in a direction of the main axis away from opposing sides of thepropeller elements.
 23. The mechanism according to claim 21 in a pumpingconfiguration.
 24. The mechanism according to claim 21 wherein there isprovided a central infill spanning a central unswept area surrounded bythe collective sweep areas of the propeller elements, the central infillbeing tapered towards opposing apexes along the main axis on opposingsides of the propeller elements.
 25. The mechanism according to claim 24in a turbine generator configuration in which the central infill housesa rotor which is coupled to the propeller elements so as to be driven byrotation of the propeller elements and wherein there is provided a powertake off mechanism for capturing power from rotation of the rotor. 26.The mechanism according to claim 25 wherein each propeller elementcomprises a plurality of blades at various positions about a fullcircumference of the propeller element, the blades of each propellerelement being rotatable in one or more planes which are offset in adirection of the main axis from the blades of adjacent propellerelements.
 27. The mechanism according to claim 26 wherein length of theblades increases in the flow direction.
 28. The mechanism according toclaim 1 wherein there is provided four propeller elements supported atevenly spaced positions about the main axis, an inner periphery of eachsweep area being intersected by the main axis.
 29. The mechanismaccording to claim 28 wherein there is provided a generally cylindricalcentral baffle intersecting the propeller axes.
 30. The mechanismaccording to claim 29 wherein there is provided a plurality of radialbaffles extending in a radial direction of the main axis and supportingthe central baffle, the radial baffles intersecting one another at themain axis.
 31. The mechanism according to claim 1 wherein the propellerelements are rotatably supported on a frame with the propeller axes infixed relation to one another and the frame, the frame being supportedfor rotation about the main axis.
 32. The mechanism according to claim 1in a turbo fan-jet compressor configuration, the mechanism furthercomprising: contoured infills enclosing an unswept area between theouter baffle and the collective sweep areas of the propeller elements,the contoured infills surrounding the collective sweep areas of thepropeller elements and being tapered on opposing sides of the propellerelements towards the outer baffle; a central infill spanning a centralunswept area surrounded by the collective sweep areas of the propellerelements, the central infill being tapered towards the main axis onopposing sides of the propeller elements; a cylindrical central baffleconcentrically spaced between the central infill and the outer baffle,the propeller axes being located at spaced positions about the centralbaffle; and a plurality of radial baffles extending in a radialdirection of the main axis between the central infill and outer bafflesand supporting the central baffle.
 33. The mechanism according to claim32 wherein each propeller element comprises a plurality of pairs ofdiametrically opposed blades which are stacked along the propeller axisat various angles relative to one another in a helical configuration,each blade having an equal angle pitch of no more than 45 degrees. 34.The mechanism according to claim 33 wherein the blades of each propellerelement lie in a common plane with corresponding blades of adjacentpropeller elements, the propeller elements being rotated together at apredetermined timing relative to one another to avoid collision ofadjacent propeller elements having overlapping sweep areas.
 35. Themechanism according to claim 1 in a polarizing unit configuration forproduction of plasma by low temperature gas fusion, the mechanismfurther comprising: a generally cylindrical inner baffle inscribedwithin an inner periphery of the collective sweep areas of therespective propeller elements; a generally cylindrical central baffleconcentrically spaced between the inner and outer baffles; and aplurality of radial baffles extending in a radial direction of the mainaxis between the inner and outer baffles and supporting the centralbaffle; at least one of the baffles including a passage for receiving acooling fluid to be circulated therethrough.
 36. The mechanism accordingto claim 35 wherein each propeller element comprises a pair ofdiametrically opposed blades, each having a pitch angle of less than 45degrees, the sweep area of each propeller element overlapping the sweeparea of adjacent propeller elements by approximately 50% of a length ofthe blades of the propeller elements.
 37. The mechanism according toclaim 35 wherein there is provided six propeller elements which aresupported for rotation within a generally common plane, rotation of eachpropeller element being fixed in timing with rotation of adjacentpropeller elements to avoid collision of the propeller elements at theoverlapping sweep areas.
 38. The mechanism according to claim 35 incombination with a sealed spherical vessel into which gases are pulsedat intermittent intervals and plasma is extracted.